RU31816U1 - NK-38ST gas turbine engine, compressor, combustion chamber, turbine - Google Patents

Description

2002130933

 1P1R | 1Sh11I11ShSh11111Sh

ZBo-ijijisST

MKI F02C3 / 00, 7/00, 7/12, 7/20,

F01D5 / 00, 11/00,

F04D17 / 00, 29/00,

F23R3 / 00

GAS-TURBINE ENGINE NK-38ST. COMPRESSOR. CAMERA

COMBUSTION. TURBINE.

The useful model relates to the field of turbine construction, and specifically to the design of industrial gas turbine engines.

Known gas turbine engine containing a compressor, a combustion chamber, a turbine, a free turbine, a frame, bearings, shells, pipelines, heat exchanger. In addition, the gas turbine engine contains an oil system, fuel supply systems, regulation, start-up, emergency shutdown, air intake, inlet gas supply (L.A. Shubenko-Shubin Gas-turbine units, M., Engineering, 1967, p. 93).

Such a gas turbine engine has little modularity, is inconvenient during transportation, and lifting equipment requires lifting mechanisms.

A known compressor of a gas turbine engine containing a rotor with a shaft, disks and rotor blades, a stator with adjustable

guide vanes, bypass valve (US Patent No. 3736070, NKI 415-147, 1973).

However, a stator with such an adjustable guide vane has significant weight and dimensions, and the bypass valve is not reliable enough.

A known combustion chamber of a gas turbine engine, comprising an outer and inner case, a flame tube, fuel manifolds, a hood, fuel burners on duty and the main zone (US Patent No. 4483149 IPC 3F02C7 / 00).

However, such a combustion chamber is not reliable enough.

A gas generator turbine is known, including high and low pressure turbines, each of which consists of a stator and a rotor with rotor blades and nozzle devices, the turbine consisting of separate modules (GHH Indastriegastturbinen FT8, Prospectus from MAN).

However, the cooling efficiency of such a turbine is insufficient.

The objective of this utility model is to increase the modularity of a gas turbine engine, reduce weight and reduce the dimensions of the compressor, increase the reliability of the bypass valve, increase the reliability of the combustion chamber, increase the cooling efficiency of the turbine.

The problem is solved due to the fact that the gas turbine engine is divided into a gas generator module and a free turbine module.

The frame of the gas turbine engine consists of two parts, from the frame of the gas generator and the frame of the free turbine. Each frame is equipped with wheel pairs and a mechanism for regulating the position of the frame relative to the base, made in the form of a screw pair.

The heat exchanger is mounted on the shell and is located in the upper part of the gas turbine engine.

The compressor is equipped with a bypass valve, in the case of which a window is made, this window is closed by an elastic plate on which a T-shaped stop with a wedge-shaped protrusion is fixed. A drive ring with a roller, which interacts with a wedge-shaped protrusion, is installed on the bypass valve body.

The compressor rotary blades are equipped with levers that are pivotally connected to the drive ring. The ring is equipped with a cylindrical protrusion and pins located on its outer surface. The protrusion is pivotally connected to the drive, and the pins with rotary blades.

Between the rotor disks and the guide vanes, sealing diaphragms with inclined and horizontal sections are installed, and the angle between them is 95-135 degrees.

The inspection hatch of the gas turbine engine housing comprises a casing fixed to the engine housing opposite the inspection window and a plug with a spring located therein. The plug is equipped with a through

a central hole, a bore, and a rod located in the hole with a conical head on the side of the body, and with the opposite - restrictive washer.

The combustion chamber of a gas turbine engine contains an outer and inner case, a flame tube, fuel manifolds, a hood, fuel burners of the standby and main zones, a flame tube and burners of the main zone are fixed to the hood.

The gas generator turbine includes separate rotor modules for high and low pressure turbines, a nozzle unit module and a turbine support module.

The working blade contains a feather with an upper cavity and a front and rear cavities separated by a longitudinal partition, having side walls equipped with parallel ribs inclined to the axis of rotation in the opposite direction from the back and trough, the ribs contacting each other at the intersection, and one end of each the ribs of the anterior cavity are connected to the septum. In addition, in the posterior cavity of the scapula, an additional longitudinal septum can be installed located between the longitudinal septum and the ribs and forming a channel with it tapering to the periphery of the pen. A deflector can be installed in the upper cavity of the scapula located at the outlet of the intercostal channels of the anterior cavity, and is formed between the deflector and the additional longitudinal partition

gap. The blade feather can be equipped with spherical recesses located on the walls of the cavities of the pen and the castle part, and the ratio of the distance between the centers of the spherical recesses to their diameter is less than 3.5.

Between the shelves of the blades of the nozzle apparatus, a gap of variable size is made.

An outlet visor with an outer and inner annular walls and a channel between them is made on the nozzle apparatus. An input visor is made on the impeller, placed under the output visor, the length of the inner annular wall being shorter than the outer one.

At the ends of the shelves of the blades of the nozzle apparatus, grooves are made in which sealing plates of a pressed wire spiral impregnated with a heat-resistant composition are installed, and the end edges of the sealing plate have the shape of a wedge. The angle of the wedge is from 30 to 90 degrees.

The coaxial shafts of the gas turbine engine, connected by means of splines, comprise a threaded sleeve with splines fixing the shafts, a spring and a locking element in contact with the splines of the sleeve and one of the shafts, the sleeve being made with a cylindrical shank on which the external splines are made and the locking element is made in in the form of a cage with external and internal slots in contact with

splines of the shaft and the sleeve, while the casing covers the shank of the sleeve and is spring loaded relative to it.

The figure 1 shows a gas turbine engine mounted on a frame. Figure 2 shows the frame of the gas generator, and figure 3 shows the frame of a free turbine. The figure 4 shows the compressor of a gas turbine engine. Figure 5 shows a longitudinal section of the bypass system, and figure 6 is a section AA of figure 5. Figure 7 schematically shows an adjustable guide apparatus of an axial compressor, a longitudinal section. Figure 8 shows a longitudinal section of an axial compressor with sealing diaphragms, and in figures 9 and 10, respectively, nodes I and II in figure 8. Figure 11 shows the inspection hatch of the compressor housing. The figure 12 shows the combustion chamber of a gas turbine engine. Figure 13 is a longitudinal section through a gas generator turbine. The figure 14 presents a longitudinal section of the working blades of the turbine of the gas generator. The figure 15 shows a longitudinal section of a part of the turbine with a nozzle apparatus. The figure 16 shows the element I in the figure 15 on an enlarged scale. The figure 17 shows a section aa in figure 15 in a scan to the surface of rotation. The figure 18 shows the seal between the sections of the nozzle apparatus of the turbine. The figure 19 shows the nozzle apparatus with grooves for the sealing plates. The figure 20 shows a section of the sealing plates and mating grooves in the original

condition, and in figure 21 is the same after compression. The figure 22 shows the connection of coaxial spline shafts.

The gas turbine engine 1 contains a compressor 2, a combustion chamber 3, a turbine 4, a free tsfbin 5, a frame 6, bearings bearings 7, shell 8, pipelines 10, a heat exchanger 11.

The engine is divided into two modules - a gas generator module 12 and a free turbine module 13.

The frame 6 of the gas turbine engine 1 consists of two parts, from the frame 14 of the gas generator and the frame 15 of the free turbine. Each part of the frame 6 is equipped with wheel pairs 16 and a mechanism 17 for regulating the position of the frame 6 relative to the base, made in the form of a screw pair 18.

The heat exchanger 11 is mounted on the shell 19 and is located in the upper part of the gas turbine engine.

The compressor 2 of the gas turbine engine 1, comprises a rotor 20 with a shaft, rotor disks 21 and rotor blades 22, a stator 23 with adjustable guide vanes 24, air bypass valves 25.

The lOianan bypass 25 contains a housing 26 with a window 27 closed by an elastic plate 28 on which a T-shaped stop 29 with a wedge-shaped protrusion 30 is fixed, and a drive ring 31 with a roller 32 that interacts with the wedge-shaped protrusion 30 is mounted on the housing 26.

Adjustable guide vanes 24 are equipped with levers 33, which are pivotally connected to the drive rings 34. The ring 34 is equipped with a cylindrical protrusion 35 and pins 36 placed on its outer surface. The protrusion 35 is pivotally connected to the drive, and the pins 36 are connected to the rotary blades.

Between the rotor disks 21 and the guide vanes 26, sealing diaphragms 37 with inclined 38 and horizontal 39 sections are installed, and the angle between them is 95-135 degrees.

The inspection hatch 40 of the gas turbine engine housing 1 comprises a casing 42 mounted on the engine housing opposite the inspection window 41 and a cap 43 located therein with a spring 44. The cap 43 is provided with a through central hole 45, a bore 46 and a shaft 47 with a conical head 48 located in the hole 45 side of the housing, and on the opposite - restrictive washer 49.

The combustion chamber 3 of a gas turbine engine comprises an outer 50 and an inner 51 of the housing, a flame tube 52, fuel manifolds 53, a hood 54, fuel burners of the standby 55 and main zone 56. The flame tube 42 is mounted on the hood 44.

The gas generator turbine 4 includes turbines of high 57 and low 58 pressures, each of which consists of a stator and a rotor with rotor blades 59 and nozzle devices 60.

The gas generator turbine 4 consists of a high-pressure turbine rotor module, a low-pressure turbine module, a nozzle apparatus module, and a turbine support module.

The working blade 59 contains a feather 61 with an upper cavity 62 and a longitudinal cavity 63 separated by a front 64 and a rear 65 cavities having side walls provided with parallel ribs 66,67,68,69 inclined to the axis of rotation in the opposite direction from the back and trough. The ribs contact each other at the intersection, and one end 70 of each rib 66 and 67 of the front cavity is connected to the partition 71.

In the rear cavity 65 of the blade 59, an additional longitudinal partition 72 is installed, located between the longitudinal partition 63 and the ribs 68.69 and forming with it a channel 73 tapering to the periphery of the pen.

A deflector 74 is installed in the upper cavity 62, located at the outlet of the intercostal channels of the anterior cavity 64, and a gap 75 is formed between the deflector 74 and the additional longitudinal partition 72.

The pen 61 is provided with spherical recesses 76 located on the walls 77 of the cavities of the pen 61 and the castle part 78.

The ratio of the distance t between the centers of the spherical recesses 76 to their diameter is less than 3.5.

spherical recesses can be staggered.

Between the shelves 79 of the blades 80 of the nozzle apparatus 60, a gap 81 of a variable size is made.

An exit visor 82 with an outer 83 and an inner 84 annular walls and a channel 85 between them is formed on the nozzle apparatus 60, and an entrance visor 87 is located on the impeller 86 and is located under the exit visor 82, the length of the inner 84 of the annular wall being less than the outer 83.

At the ends 88 of the shelves 79 of the blades 80 of the nozzle apparatus 60, grooves 89 are made, into which the sealing plates 90 are made of a pressed wire spiral impregnated with a heat-resistant composition, the end edges of the sealing plate having the shape of a wedge, the wedge angle is from 30 to 90 degrees.

The coaxial splined shafts 91 and 92 (FIG. 22) of the gas turbine engine 1, connected by splines 93, are fixed by a threaded sleeve 94. It is screwed into the shaft 92 and prevents the axial displacement of the shaft 91 with its collar 95. The sleeve 96 covers the cylindrical shank of the threaded sleeve 94 and engages with slots 97 and 98 made at its end with slots 99 and 100 of the threaded sleeve 94 and the shaft 91. The clip 96 is spring loaded relative to the threaded sleeve 94 by a spring 101 resting on the washer 102 and the spring split ring 103. The movement of the clip is limited by the ring 104, hard to connected with her.

1ZHI1ShZZ

10

The gas turbine engine 1 operates as follows. Air is compressed by compressor 2 and supplied to combustion chamber 3, where natural gas is also supplied, the thermal energy obtained in this case in turbine 4 and in free turbine 5 is converted into mechanical energy. The gas generator turbine 4 drives the compressor 2, and the free turbine 5 is used to rotate the drive mechanism (natural gas supercharger).

Transportation and storage of the gas turbine engine 1 is carried out on frames 14.15 in containers. The movement of the gas turbine engine 1 and its modules 12, 13 during installation, alignment with the drive mechanism and the docking of the gas generator module 12 with the free turbine module 13 is carried out using wheel pairs 16, mechanisms 17,18.

The heat exchanger 11 (figure 1) is designed to cool the air taken from the compressor 2 for cooling the blades of the turbine 4. As a cooler, fuel gas is used.

During operation of the gas turbine engine 1, the flow from the cavity of the compressor 2 enters the housing 26 of the bypass valve 25 (Fig. 5,6). By the forces of the elastic plate 28 and the differential pressure, the elastic plate 28 is pressed against the surface of the housing 26, blocking the window 27. After the command to open the valve, rotate the drive ring 31 relative to the housing 26. The rotating ring 31 moves the rollers 32, which are rolling

According to the wedge-shaped holder 30 of the T-shaped stop 29, the elastic plate 28 is moved inside the valve body 26, and the air from the compressor is transferred to the atmosphere into the resulting gap.

Adjustable guiding devices 24 (Fig. 7) change the angular position when the drive rings 34 are rotated and the levers 33, pivotally connected thereto,

When the compressor is operating in the gap between the rotor disks 21 (Fig. 8-10) and the guide vanes 26, stable eddies with a swirl in the main flow direction are formed in sections 38 and 39 of the sealing diaphragm 37. The flow glides along these vortices with virtually no loss of energy.

Air from the compressor 2 enters the combustion chamber 3 (Fig. 12) into the burners of the standby and main zones. First, the fuel is fed into the fuel burners of the duty zone 55, and then, after ignition and reaching the specified temperature mode, the fuel burners of the main zone 56.

During operation of the turbine 4 (Fig. 13), hot gas heats the working blades 59 and the blades 60 of the nozzle apparatus of the turbine. To cool the blades 59, the air drawn from the compressor enters the front cavity 64 (Fig. 14) flows between the ribs 66.67, cooling the inlet edge and the walls of the cavity 64 of the blade 59, from where it enters the upper cavity 62, turns around with a deflector 74, and flows around an additional partition 72 and along the channels between the ribs 68.69

is discharged through the outlet edge into the flow part of the turbine. Part of the air through the gap 75 between the end of the additional partition 72 and the deflector 74 is passed directly to the rear cavity 65, additionally cooling the peripheral part of the blade 59. When cooling air moves above the spherical recesses 76, a system of vortices emanating from the recesses 76 is formed, which increases the cooling efficiency of this section of the pen .

When the blades of the nozzle apparatus are heated, the gaps 81 (FIG. 17) are selected. However, the presence of a gap 81 increasing in the direction of gas flow in the section from flanges to the ends of the shelves 79 eliminates the contact of thin sections of the shelves 79 that arise due to deformation of the blades during operation and the selection of backlash due to gas forces.

The cooling air flowing out of the channel 85 (FIG. 16) closes the slit formed by the inner wall 84 and the inlet visor 82 preventing the air from flowing from under the inlet visor 82 into the gas stream, and then a portion of the inlet visor 82 flows into the turbine flow path, forming a film protection of the end surfaces of the interscapular channels of the impeller,

Sealing plates 90 (FIGS. 18-21) are installed in grooves 89 and crimped before assembly. During engine operation, due to thermal deformations, there is a choice of the gaps between the ends of the shelves 79 and the complete compression of the sealing plate 90,

about

thirteen

At the same time, the sealing plate 90 fits snugly against the surface of the grooves 89 over the entire width, compensating for the non-parallelism and other manufacturing and installation inaccuracies.

The connection of coaxial spline shafts (Fig. 22) is as follows.

A sleeve 96 is preliminarily put on a sleeve 96, a spring 101, a washer 102, a ring 103 and 104.

Then put the shaft 91 on the shaft 92 so that the slots engage and screw the sleeve 94 into the shaft 92, while moving the clip 96 to the left, compressing the spring 101. The sleeve 94 is screwed in until it stops, after which the clip 96 is released, which is used by the spring 101 moves to the right and engages with the splines of the shaft 91.

Using the utility model on the NK-38ST engine allowed: to repair individual components in the factory; to replace the engine and its individual parts without the use of lifting mechanisms;

in the compressor path to reduce overflow into the connected volumes;

simplify the design of the bypass valve; reduce the weight of the adjustable guide vane; dispense with special pendants of the combustion tube combustion tube;

14

INCREASE the cooling intensity of the working blades and nozzle apparatus of the Turbine;

simplify the installation of coaxial shafts.

5,

fifteen

Claims (21)

1. A gas turbine engine comprising a compressor, a combustion chamber, a turbine, a free turbine, a frame, an emergency shutdown system, characterized in that the engine is divided into a gas generator module and a free turbine module. 2. The gas turbine engine according to claim 1, characterized in that the gas turbine engine frame consists of a gas generator frame and a free turbine frame. 3. The gas turbine engine according to claim 2, characterized in that each frame is equipped with wheel pairs. 4. The gas turbine engine according to claim 2, characterized in that the frame is equipped with a mechanism for regulating the position of the frame relative to the base, made in the form of a screw pair. 5. The gas turbine engine according to claim 1, characterized in that its coaxial shafts connected by splines comprise a threaded sleeve with splines fixing the shafts, a spring and a locking element in contact with the splines of the sleeve and one of the shafts, the sleeve being made with a cylindrical shank on which the external slots are made, and the locking element is made in the form of a cage with external and internal slots in contact with the splines of the shaft and the sleeve, while the casing covers the shaft of the sleeve and the spring relative to it. 6. The gas turbine engine according to claim 1, characterized in that its heat exchanger is mounted on the shell and placed in the upper part of the engine. 7. A compressor comprising a rotor with a shaft, disks and rotor blades, a stator with adjustable guide vanes, air bypass valves, characterized in that the bypass valve comprises a housing with a window closed by an elastic plate on which a T-shaped stop with a wedge-shaped protrusion is fixed, and on the case there is a drive ring with a roller that interacts with a wedge-shaped protrusion. 8. The compressor according to claim 7, characterized in that the rotary blades are equipped with levers that are pivotally connected to a drive ring equipped with a cylindrical protrusion and pins located on its outer surface, the protrusion being pivotally connected to the drive, and the pins through levers with rotary blades . 9. The compressor according to claim 7, characterized in that between the rotor disks and the guide vanes are installed sealing diaphragms with inclined and horizontal sections, and the angle between them is 95-135 °. 10. The compressor according to claim 7, characterized in that the inspection hatch of the gas turbine engine housing comprises a casing fixed to the engine housing opposite the inspection window and a cap with a spring located therein, the cap being provided with a through central hole with a bore and a conical head located in the hole from the side of the case, and from the opposite side by a restrictive washer. 11. A combustion chamber comprising an outer and inner case, a heat pipe, fuel manifolds, fuel burners of the standby and main zones, characterized in that the heat pipe and burners of the main zone are mounted on the hood, which is mounted on the outer case. 12. A turbine comprising high and low pressure turbines, each of which consists of a stator with nozzle apparatuses and a rotor with rotor blades, characterized in that the rotor blade contains a pen with an upper cavity and a front and rear cavities separated by a longitudinal partition having side walls equipped with parallel ribs inclined to the axis of rotation in the opposite direction from the back and trough, the ribs contacting each other at the intersection, and one end of each rib of the front cavity connected to the partition. 13. The turbine according to claim 12, characterized in that an additional longitudinal partition is installed in the posterior cavity of the scapula located between the longitudinal partition and the ribs and forming a channel narrowing to the periphery of the pen. 14. The turbine according to claims 12 and 13, characterized in that a deflector is installed in the upper cavity located at the outlet of the intercostal channels of the anterior cavity, and a gap is formed between the deflector and the additional partition. 15. The turbine according to claims 12-14, characterized in that the pen is provided with spherical recesses located on the walls of the cavities of the pen and the castle part. 16. The turbine of claim 15, wherein the ratio of the distance between the centers of the spherical recesses to their diameter is less than 3.5. 17. The turbine according to p. 16, characterized in that on the inner surface of the hollow feather of the working blades made spherical recesses located in a checkerboard pattern. 18. The turbine according to item 12, characterized in that between the shelves of the blades of the nozzle apparatus a clearance of a variable value is made. 19. The turbine according to p. 18, characterized in that the nozzle device has an output visor with an outer and inner annular walls and a channel between them, and on the impeller there is an input visor located under the output visor of the nozzle device, the length of the inner ring wall being less than the outside. 20. The turbine according to claim 12, characterized in that grooves are made in the ends of the shelves of the blades of the nozzle apparatuses, into which the sealing plates of a pressed wire spiral impregnated with a heat-resistant composition are installed, the end edges of the sealing plate having the shape of a wedge. 21. The turbine according to claim 20, characterized in that the wedge angle is from 30 to 90 °.